Aerospace Science and Technology最新文献_第8页

Comprehensive analysis and performance optimization of different control parameters on an aviation heavy-fuel rotary engine 航空重燃料旋转发动机不同控制参数的综合分析与性能优化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-02-04 DOI: 10.1016/j.ast.2026.111853

Rui Liu , Siyu Liu , Zirui Fang , Jing Li , Lingfeng Zhong , Shen Xue

With the rapid development of the low-altitude economy and unmanned aerial vehicle (UAV) technology, aviation heavy-fuel rotary engines have re-emerged as a key power system, making the optimization of their control parameters crucial. This study established one-dimensional (1-D) and three-dimensional (3-D) numerical simulation models of an aviation heavy-fuel rotary engine, validated with experimental data, to investigate the effects of start of injection (SOI), injection pressure (P_inj), and trailing spark plug ignition timing (θ_ign) on the mixture formation, combustion, and emission. Results show that retarding SOI improves mixture homogeneity and reduces soot, while higher P_inj concentrates fuel in the chamber front, creating an over-rich zone. Advancing θ_ign causes a non-monotonic change in peak in-cylinder pressure (P_max), underscoring the need for careful timing selection. Based on these findings, the entropy weight technique for order preference by similarity to ideal solution (EW-TOPSIS) was employed to identify the optimal control scheme: SOI = –500°EA ATDC, P_inj = 0.3 MPa, and θ_ign = –10°EA ATDC. This configuration boosts P_max by 11.08 %, increases indicated mean effective pressure (IMEP) by 14.69 %, and reduces soot emissions by 42.14 % compared to the original scheme.

随着低空经济和无人机技术的快速发展，航空重燃料旋转发动机作为关键动力系统重新崛起，其控制参数的优化变得至关重要。本文建立了航空重燃油旋转发动机的一维（1-D）和三维（3-D）数值模拟模型，并通过实验数据进行验证，研究了喷射启动（SOI）、喷射压力（Pinj）和尾部火花塞点火正时（θign）对混合气形成、燃烧和排放的影响。结果表明：缓速SOI改善了混合气的均匀性，减少了烟尘，而较高的Pinj使燃料在燃烧室前部集中，形成过富区；推进θign会导致峰值缸内压力（Pmax）的非单调变化，强调需要仔细选择定时。在此基础上，采用近似理想解排序偏好熵权法（EW-TOPSIS）确定了最优控制方案：SOI = -500°EA ATDC, Pinj = 0.3 MPa, θign = -10°EA ATDC。与原方案相比，该方案使Pmax提高了11.08%，平均有效压力（IMEP）提高了14.69%，烟尘排放量减少了42.14%。

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引用次数: 0

Local obstacle avoidance and trajectory tracking control of multi-quadrotor cooperative transportation system 多四旋翼协同运输系统的局部避障与轨迹跟踪控制

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-29 DOI: 10.1016/j.ast.2026.111670

Jinlong Sun, Dong Zhang, Yuhe Chen, Lingzhi Mu, Guangyu Jia

Compared with ground transportation and single quadrotor transportation, multi-quadrotor cooperative transportion can not only carry heavier cargo, but also significantly improve fault tolerance and stability. This paper presents a local obstacle avoidance and trajectory tracking control method for a multi-quadrotor cooperative transportation system (MQCTS). Firstly, a combined modeling approach is used, quadrotors and payload dynamics models are established respectively, and the cable tension is solved using the Udwadia-Kalaba equation. Secondly, combined with multi-agent formation, a virtual leader structure and a symmetric formation generation strategy based on inter-agent safety distance are adopted. Thirdly, a novel predefined-time nonlinear disturbance observer (PTNDO) is proposed to estimate the lumped disturbances, and a predefined-time adaptive sliding mode controller (PTASMC) is designed to improve the response speed. Fourthly, a local obstacle avoidance method based on artificial potential field and formation switching strategy (APF-FSS) is designed, achieving local obstacle avoidance and passage through narrow gaps. Finally, the simulation results show that the designed control strategy can effectively improve the system’s response speed and robustness, and the proposed local obstacle avoidance method enhances environmental adaptability and significantly improves transportation efficiency.

与地面运输和单四旋翼运输相比，多四旋翼协同运输不仅可以承载更重的货物，而且可以显著提高容错性和稳定性。提出了一种多四旋翼协同运输系统的局部避障与轨迹跟踪控制方法。首先，采用组合建模方法，分别建立了四旋翼和载荷动力学模型，利用Udwadia-Kalaba方程求解了索张力；其次，结合多智能体编队，采用虚拟领导者结构和基于智能体间安全距离的对称编队生成策略；第三，提出了一种新的预定义时间非线性扰动观测器（PTNDO）来估计集总扰动，并设计了一个预定义时间自适应滑模控制器（PTASMC）来提高响应速度。第四，设计了一种基于人工势场和编队切换策略（APF-FSS）的局部避障方法，实现了车辆的局部避障和窄间隙通行。仿真结果表明，所设计的控制策略能有效提高系统的响应速度和鲁棒性，提出的局部避障方法增强了环境适应性，显著提高了运输效率。

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引用次数: 0

Unsteady aerodynamics of elastic avian-inspired morphing wing during the folding process 弹性变形翼折叠过程中的非定常空气动力学

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-29 DOI: 10.1016/j.ast.2026.111776

Haibo Zhang , Haolin Yang , Qi Dang , Guanghan Wang , Chen Song , Chao Yang

This paper presents an aeroelastic analysis and aerodynamic load prediction framework for elastic avian-inspired morphing wings, in which the time-varying features of structural folding are added to the simulation. The framework uses the viscous vortex particle method to establish the unsteady aerodynamic model, and parameterizes the structural dynamic model by manifold tangent space interpolation. The transient response of the time-varying structure is solved through time finite element formulations. A wing prototype is manufactured for wind tunnel testing to initially validate the effectiveness of the method proposed, verifying that the prediction error of unsteady aerodynamic loads of our method is not more than 8.9% compared with the experimental data. The result shows that the in-plane folding process will cause the actual aerodynamic loads to deviate from the steady state and the hysteresis loop in lift response, which depends on the folding direction and the morphing rate.

本文提出了一种将结构折叠时变特征加入仿真的弹性仿鸟翼气动弹性分析和气动载荷预测框架。该框架采用粘性涡质点法建立非定常气动模型，并通过流形切空间插值将结构动力学模型参数化。采用时间有限元方法求解时变结构的瞬态响应。通过制造机翼样机进行风洞试验，初步验证了所提方法的有效性，验证了所提方法对非定常气动载荷的预测误差与实验数据相比不超过8.9%。结果表明，平面内折叠过程会导致实际气动载荷偏离稳态，并导致升力响应的滞后环，这与折叠方向和变形速率有关。

引用次数: 0

Gaussian process-driven uncertainty quantification of labyrinth seal aero-thermal performance 高斯过程驱动的迷宫密封气动热性能不确定性量化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-29 DOI: 10.1016/j.ast.2026.111796

Xiang Zhang, Decheng Xu, Yifan Cao, Wanting Yu, Zhongzhi Zhang

Manufacturing tolerances introduce geometric uncertainties that significantly impact the performance reliability of labyrinth seals, yet systematic quantification of these effects remains largely unexplored. This study develops a Gaussian Process-driven uncertainty quantification (UQ) framework, leveraging a high-fidelity surrogate model (R² > 0.998) trained on CFD simulations to analyze how 35 geometric variations impact leakage and windage heating. A systematic asymmetric performance drift is revealed: under realistic Gaussian-distributed tolerances, the mean mass flow rate decreases by 0.43% while the mean temperature rise increases by 0.21%, establishing a fundamental performance trade-off. Variance-based global sensitivity analysis identifies tip clearances as the decisive factor, accounting for over 85% of performance variance, with the final-stage clearance (s4) being most critical. The mechanism behind this trade-off is twofold: leakage is governed by monotonic throttling, while temperature rise follows a non-monotonic energy balance where minimum clearance combines near-peak heating with minimal cooling flow, creating the highest thermal risk. The findings provide quantitative guidance for robust design—demonstrating that tightening clearance tolerances by 30% reduces performance variance by approximately 50%—and establish the theoretical foundation for uncertainty-based tolerance allocation in high-performance turbomachinery sealing systems.

制造公差引入几何不确定性，极大地影响了迷宫密封的性能可靠性，但这些影响的系统量化在很大程度上仍未得到探索。本研究开发了一个高斯过程驱动的不确定性量化（UQ）框架，利用经过CFD模拟训练的高保真替代模型（R²> 0.998）来分析35种几何变化对泄漏和窗口加热的影响。系统的非对称性能漂移：在真实的高斯分布容差下，平均质量流量下降0.43%，平均温升上升0.21%，形成了基本的性能权衡。基于方差的全局敏感性分析将尖端间隙确定为决定性因素，占性能差异的85%以上，其中最后阶段间隙（s4）最为关键。这种权衡背后的机制是双重的：泄漏由单调节流控制，而温度上升遵循非单调能量平衡，最小间隙结合近峰值加热和最小冷却流量，产生最高的热风险。研究结果为稳健设计提供了定量指导，表明30%的拧紧间隙公差可减少约50%的性能差异，并为高性能涡轮机械密封系统中基于不确定性的公差分配奠定了理论基础。

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引用次数: 0

A divide-and-conquer machine learning transition model for airfoil flows: From steady linear-lift to unsteady stall stage 一个分而治之的机器学习过渡模型的翼型流动：从稳定的线性升力到非定常失速阶段

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-02-01 DOI: 10.1016/j.ast.2026.111778

Lei Wu , Tianyuan Liu , Zuoli Xiao

In this paper, a steady/unsteady integrated machine learning transition model is established via the divide-and-conquer (DaC) strategy, which covers a wide operating range of an airfoil from linear lift to deep stall. To consider the essential distinctions across different regions of the entire flow domain, a random forest binary classifier is adopted to detect the flow field as either intermittent spot or non-intermittent spot region. Two transitional intermittency factor regressors are crafted respectively within their own regions, thus facilitating the capture of crucial phenomenological details. Three airfoil geometries with different angles of attack, Mach numbers and Reynolds numbers are selected to fully validate the newly developed DaC model. The a posteriori results demonstrate that the DaC model aligns well with its benchmark counterpart across the full range of angles of attack, and can overcome the limitations of Non-DaC model in the stall stage of an airfoil frequently characterized by unsteady behavior. This divide-and-conquer-guided framework may advance the application of machine learning-based transition model to the airfoil design engineering, and potentially establish a generalizable strategy for modeling complex physics scenarios.

本文采用分而治之（DaC）策略建立了一个定/非定常集成机器学习过渡模型，该模型涵盖了翼型从线性升力到深度失速的广泛工作范围。为了考虑整个流域不同区域之间的本质区别，采用随机森林二值分类器对流场进行间歇点区域和非间歇点区域的检测。两个过渡性间歇因子回归因子分别在各自的区域内制作，从而促进了关键现象学细节的捕捉。选择三种不同迎角、马赫数和雷诺数的翼型几何形状来充分验证新开发的DaC模型。后验结果表明，DaC模型在全迎角范围内与基准模型一致，克服了非DaC模型在非定常翼型失速阶段的局限性。这种分而治之的指导框架可以推进基于机器学习的过渡模型在翼型设计工程中的应用，并有可能为复杂物理场景的建模建立一种可推广的策略。

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引用次数: 0

Research on coupled aerodynamic characteristics for ducted rotor system of a deflectable land-air platform under duct deflection and ground effects 风道偏转和地面效应作用下可偏转陆空平台导管转子系统耦合气动特性研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-26 DOI: 10.1016/j.ast.2026.111770

Qingkai Meng , Wei Wei , Zhifang Ke , Yongjie Shu , Shiyi Wei , Xixing Long , Maofeng Zhang , Qingdong Yan

Low-altitude ground effect combined with rotor deflection introduces unpredictable disturbances to the aerodynamic performance and stability of the ducted rotor propulsion system. To achieve safe take-off and landing of a deflectable land–air platform, the influences of the ground effect, the deflection effect, and their coupling on the system stability during take-off and landing were explored. The aerodynamic performance analysis of the ducted rotor system under different deflection angles θ and ground clearance Z/R (height to radius ratio) was carried out, and bench tests were carried out for verification. The results show that the ground effect significantly enhances the lift in the range of Z/R < 3. Under the condition close to the ground (Z/R < 1.5), as the deflection angle θ increases, the lift coefficient decreases significantly. The increase in the deflection angle will weaken the thrust gain brought by the ground effect, and the interaction between the two shows obvious coupling characteristics. Furthermore, a thrust-to-weight ratio prediction model including the height disturbance term and the deflection correction term were constructed. The model showed good fitting accuracy (R²>0.98) under all conditions, and the near-ground lift contour considering the deflection was obtained. The related work can provide a control boundary reference for the safe takeoff and landing of the deflection-type land-to-air platform, and the research results can provide a theoretical basis for the take-off and landing and cross-domain process control strategies of related land-to-air platforms.

低空地面效应和旋翼偏转对导管式旋翼推进系统的气动性能和稳定性造成不可预测的干扰。为实现可偏转地空平台的安全起降，研究了地面效应、偏转效应及其耦合对系统起降稳定性的影响。对导管式转子系统在不同偏转角θ和离地间隙Z/R（高半径比）下的气动性能进行了分析，并进行了台架试验验证。结果表明：在Z/R<范围内，地面效应显著提高了升力；在接近地面的条件下（Z/R < 1.5），随着挠度角θ的增大，升力系数显著减小。挠度角的增大会减弱地面效应带来的推力增益，两者的相互作用表现出明显的耦合特性。在此基础上，建立了包含高度扰动项和偏转修正项的推重比预测模型。在所有条件下，模型均具有良好的拟合精度（R2>0.98），得到了考虑挠度的近地扬程轮廓。相关工作可为偏转型地空平台安全起降提供控制边界参考，研究成果可为相关地空平台的起降及跨域过程控制策略提供理论依据。

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引用次数: 0

Dual-layer model predictive control for autonomous capture of failed targets under complex obstacle conditions 微波火箭异常放电形成的观测及其对推力性能的定量影响

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-05 DOI: 10.1016/j.ast.2025.111572

Chuanxiao Xu, Guohua Kang, Zhen Li, Jiaqi Wu, Jiayi Zhou, Can Hao, Junfeng Wu

The complex surface configuration, tumbling motion, and surrounding debris environment of failed spacecraft pose significant risks and challenges to on-orbit capture and servicing missions. To ensure both safety and mission success under such conditions, this paper proposes a dual-layer model predictive control (MPC) strategy. In the upper layer, a Control Lyapunov Function (CLF) is employed to guarantee convergence, while a relaxation variable is introduced to prevent overly strict constraints, ensuring fast and flexible convergence of relative position and attitude. In the lower layer, Control Barrier Functions (CBFs) are used to impose strict safety constraints on multiple dynamic obstacles. A deadlock detection and adaptive reference adjustment mechanism is introduced between the two layers to effectively avoid local optima. Simulations under multiple initial conditions demonstrate that the proposed method achieves millimeter-level position accuracy and 0.03° attitude synchronization, while effectively avoiding collisions with the target body, solar panels, and debris under external disturbances. The approach maintains near-global optimality while emphasizing safety, providing a feasible and robust solution for micro-nano satellite on-orbit servicing missions.

失效航天器复杂的表面结构、翻滚运动和周围碎片环境对在轨捕获和维修任务构成了重大风险和挑战。为了保证在这种情况下的安全和任务成功，本文提出了一种双层模型预测控制（MPC）策略。上层采用Control Lyapunov Function （CLF）保证收敛，同时引入松弛变量防止约束过于严格，保证了相对位置和姿态的快速灵活收敛。在下层，控制障碍函数（cbf）用于对多个动态障碍物施加严格的安全约束。在两层之间引入了死锁检测和自适应参考调整机制，有效地避免了局部最优。多个初始条件下的仿真结果表明，该方法能够实现毫米级的定位精度和0.03°的姿态同步，同时有效避免了在外界干扰下与目标体、太阳能电池板和碎片的碰撞。该方法在强调安全性的同时保持了接近全局的最优性，为微纳卫星在轨服务任务提供了可行和稳健的解决方案。

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引用次数: 0

Novel design method for tilting electric-drive ducted fan blades with dual-operation conditions 双工况倾斜电驱动风管风扇叶片设计新方法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-27 DOI: 10.1016/j.ast.2026.111786

Zhezhe Su, Bo Zhang, Jianfeng Zhu, Yancheng You

With the rapid development of vectored electric vertical take-off and landing (eVTOL) aircraft, tilting electric-drive ducted fans have become the primary propulsion solution due to their high efficiency and versatility. However, thrust requirements vary significantly between takeoff and cruise phases. Conventional blade designs based on a single operating point are unable to achieve optimal performance in both conditions while accounting for motor characteristics. To address the coupling effects between blades and the motor and meet the requirements of dual-operation conditions, this paper proposes a rapid design and optimization methodology. An inverse design method based on the S2/S1 stream surface streamline curvature approach was developed. Under the constraints of blade surface pressure distribution, this method accurately determines camber line control parameters at different spanwise positions to enable precise blade design. Compared with conventional empirical model-based design approaches, the proposed method achieves a maximum reduction of 11.09% in design total pressure ratio error and a 1.60% improvement in adiabatic efficiency. Building upon this foundation, an optimization framework integrating a BP neural network surrogate model with a multi-objective genetic algorithm was implemented. By applying performance constraints under both takeoff and cruise conditions, dual-condition optimization was conducted. The results demonstrate that, under takeoff and cruise conditions, the optimized blades exhibit only 2.4% and 1.0% reductions in integrated electrical efficiency compared to single-point design blades, respectively, demonstrating significantly optimized dual-condition adaptability.

随着矢量电动垂直起降（eVTOL）飞机的快速发展，倾斜式电驱动导管风扇以其高效率和通用性成为主要的推进方案。然而，推力要求在起飞和巡航阶段之间有很大的不同。考虑到电机特性，基于单一工作点的传统叶片设计无法在两种条件下实现最佳性能。为了解决叶片与电机之间的耦合效应，满足双工况的要求，本文提出了一种快速设计与优化方法。提出了一种基于S2/S1流面流线曲率法的反设计方法。该方法在叶片表面压力分布的约束下，精确确定不同展向位置的弧度线控制参数，实现叶片的精确设计。与传统的基于经验模型的设计方法相比，该方法的设计总压比误差最大减小11.09%，绝热效率提高1.60%。在此基础上，实现了BP神经网络代理模型与多目标遗传算法相结合的优化框架。同时考虑起飞和巡航条件下的性能约束，进行双工况优化。结果表明，在起飞和巡航条件下，与单点设计叶片相比，优化后的叶片的综合电效率分别仅降低2.4%和1.0%，显示出显著优化的双工况适应性。

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引用次数: 0

Convective flux analysis on the propagation mechanism of oblique detonation waves 斜爆震波传播机理的对流通量分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-22 DOI: 10.1016/j.ast.2026.111755

Yunfeng Liu

The aim of this study is to investigate the propagation mechanism of oblique detonation waves using the vector flux analysis method through numerical simulations. A two-dimensional numerical study is conducted on stoichiometric hydrogen-air oblique detonation waves based on the conservative Euler equations and a one-step global chemical reaction model. The wedge angle is 25°, with a freestream static temperature of 851.5 K, velocity of 2473.4 m/s, and pressure of 42.5 kPa. The motion mechanism of transverse waves is analyzed using the vector flux method. The results show that the oblique detonation front consists of three regions: an induction zone, an overdriven detonation zone, and a transverse-wave region. Under different activation energies, only either upward-propagating or downward-propagating transverse waves exist on the oblique detonation front; the two do not occur simultaneously. At low activation energy, downward-propagating transverse waves dominate, whereas at high activation energy, upward-propagating transverse waves appear.

本文采用矢量通量分析方法，对斜爆震波的传播机理进行了数值模拟研究。基于保守欧拉方程和一步全局化学反应模型，对化学计量氢-空气斜爆震波进行了二维数值研究。楔形角为25°，自由流静态温度851.5 K，流速2473.4 m/s，压力42.5 kPa。用矢量通量法分析了横波的运动机理。结果表明，斜爆轰锋面由感应区、超驱动区和横波区三个区域组成。在不同活化能下，斜爆轰前缘只存在向上传播或向下传播的横波；这两者不会同时发生。在低活化能时，以向下传播的横波为主，而在高活化能时，以向上传播的横波为主。

引用次数: 0

Priority-enhanced INDI for over-actuated systems: stability and robustness analysis 过度驱动系统的优先级增强INDI：稳定性和鲁棒性分析

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-06-01 Epub Date: 2026-01-22 DOI: 10.1016/j.ast.2026.111624

Chaoheng Meng , Hailong Pei , Zihuan Cheng , Peiye Huang

The Incremental Nonlinear Dynamic Inversion (INDI) control exhibits strong robustness and disturbance rejection ability for nonlinear systems. However, when applied to input-constrained over-actuated systems, solving the INDI control law involves complex control allocation, while existing stability analyses are often conservative. To address this issue, this paper proposes a priority-enhanced INDI (PINDI) control scheme, incorporating a prioritized control allocation method. Specifically, the proposed PINDI prioritizes allocating control authority to the trim-control term, which inherently includes disturbances and nonlinearities, to ensure the desired linearization effect. Subsequently, the error-feedback term is allocated with secondary priority to preserve dynamic effectiveness. The stability and robustness of the closed-loop system under PINDI control are further analyzed, in which weaker stability conditions are obtained compared to existing research. The theoretical findings can be generalized to INDI control frameworks equipped with arbitrary control allocation methods under input constraints, providing new theoretical foundations for filter design, controller tuning and actuator configuration. Finally, simulation and real-world flight tests are conducted using a ducted fan UAV platform with a redundant actuator configuration. The results verify that the proposed PINDI achieves significant improvement over traditional INDI schemes in terms of disturbance rejection ability and tracking performance.

增量式非线性动态反演（INDI）控制对非线性系统具有较强的鲁棒性和抗扰能力。然而，当应用于输入受限的过驱动系统时，求解INDI控制律涉及复杂的控制分配，而现有的稳定性分析往往是保守的。为了解决这一问题，本文提出了一种优先级增强的INDI （PINDI）控制方案，该方案结合了优先级控制分配方法。具体而言，所提出的PINDI优先将控制权限分配给固有包含干扰和非线性的trim-control项，以确保期望的线性化效果。然后，将误差反馈项分配二级优先级，以保持动态有效性。进一步分析了PINDI控制下闭环系统的稳定性和鲁棒性，得到了较弱的稳定条件。理论研究结果可推广到输入约束下任意控制分配方法的INDI控制框架，为滤波器设计、控制器整定和执行器配置提供新的理论依据。最后，利用具有冗余作动器配置的导管风扇无人机平台进行了仿真和实际飞行试验。实验结果表明，该方法在抗干扰能力和跟踪性能上都比传统的INDI方法有了显著提高。

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引用次数: 0